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- - **Problem with rhoSimplecFoam - nan**
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Problem with rhoSimplecFoam - nan2 Attachment(s)
Hello all,
I am trying to evolve my incompressible, steady-state 2D airfoil simulation into a compressible, steady-state simulation. I have selected rhoSimplecFoam as a solver, however I cannot get the simulation to run past 9 iterations without getting "nan" for the residuals first with k and omega, then the next iteration has residuals of "nan" for all variables. I have tried playing with the boundary conditions and solver parameters to no avail. Would someone please suggest where I could start looking? Some information: 1. The simulation runs successfully and with results that compare well to experimental data in simpleFoam; 2. The mesh is a c-grid with ~42000 cells and a boundary 10c from the NACA 0012 airfoil; 3. Angle of attack is 13 degrees, implemented by introducing a inlet velocity at that angle (mesh pic attached); 4. Boundary conditions are as attached; 5. k-omega turbulence model; 6. fvSolution & fvSchemes copied from tutorial rhoSimplecFoam\squareBend. Thank you for any suggestions, Dan |

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